EP3045672B1 - Cooling passages for a mid-turbine frame - Google Patents
Cooling passages for a mid-turbine frame Download PDFInfo
- Publication number
- EP3045672B1 EP3045672B1 EP16151372.6A EP16151372A EP3045672B1 EP 3045672 B1 EP3045672 B1 EP 3045672B1 EP 16151372 A EP16151372 A EP 16151372A EP 3045672 B1 EP3045672 B1 EP 3045672B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- frame case
- swirler tube
- gas turbine
- inner frame
- branch
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000001816 cooling Methods 0.000 title claims description 35
- 239000012530 fluid Substances 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 7
- 238000004891 communication Methods 0.000 claims description 6
- 238000012546 transfer Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 5
- 238000003754 machining Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present disclosure relates generally to a gas turbine engine, and in particular to a mid-turbine frame (MTF) included in a gas turbine engine.
- MTF mid-turbine frame
- a gas turbine engine typically includes a fan section, a compressor section, a combustor section, and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section.
- a mid-turbine frame is positioned between a high pressure turbine stage and a low pressure turbine stage of a gas turbine engine.
- the MTF supports one or more bearings and transfers bearing loads from an inner portion of the gas turbine engine to an outer engine frame.
- the MTF also serves to route air from the high pressure turbine stage to the low pressure turbine stage.
- the present invention provides a gas turbine engine in accordance with claim 1.
- the swirler tube extends in a circumferential direction.
- the circumferential direction is directed at between 50 and 80 degrees relative to a radial direction.
- the swirler tube is directed radially inward at an angle between 15 and 45 degrees.
- the swirler tube includes an outlet directed radially inward at an angle between 75 and 85 degrees to a radial direction.
- the swirler tube includes an inlet having a first cross sectional area and an out let having a second cross-sectional area.
- the second cross-sectional area is larger than the first cross-sectional area.
- a restricting ring is located in at least one branch.
- At least one branch extends in the axial direction and includes a portion with a reduced diameter for metering the cooling airflow through at least one branch.
- the present invention provides a method in accordance with claim 9.
- the method includes directing the cooling airflow in a circumferential direction.
- the swirler tube includes an inlet having a first cross sectional area and an out let having a second cross sectional area with the second cross sectional area being larger than the first cross sectional area.
- FIG. 1 schematically illustrates a gas turbine engine 20.
- the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
- Alternative engines might include an augmentor section (not shown) among other systems or features.
- the fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28.
- the exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
- the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46.
- the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30.
- the high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54.
- a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54.
- a mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46.
- the mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28.
- the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
- the core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded over the high pressure turbine 54 and low pressure turbine 46.
- the mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C.
- the turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
- gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28, and fan section 22 may be positioned forward or aft of the location of gear system 48.
- the engine 20 in one example is a high-bypass geared aircraft engine.
- the engine 20 bypass ratio is greater than about six (6:1), with an example embodiment being greater than about ten (10:1)
- the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 (2.3:1)
- the low pressure turbine 46 has a pressure ratio that is greater than about five.
- the engine 20 bypass ratio is greater than about ten (10:1)
- the fan diameter is significantly larger than that of the low pressure compressor 44
- the low pressure turbine 46 has a pressure ratio that is greater than about five (5:1).
- Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
- the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 (2.3:1). It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
- the fan section 22 of the engine 20 is designed for a particular flight condition -- typically cruise at about 0.8 Mach (274 m/s) and about 35,000 feet (10,668 m).
- "Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
- the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45 (1.45:1).
- "Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram °R) / (518.7 °R)] 0.5 .
- the "Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft / second (350.5 meters/second).
- the example gas turbine engine includes fan 42 that comprises in one non-limiting embodiment less than about 26 fan blades. In another non-limiting embodiment, fan section 22 includes less than about 20 fan blades. Moreover, in one disclosed embodiment low pressure turbine 46 includes no more than about 6 turbine rotors. In another non-limiting example embodiment low pressure turbine 46 includes about 3 turbine rotors. A ratio between number of fan blades 42 and the number of low pressure turbine rotors is between about 3.3 and about 8.6 (about 3.3:1 and about 8.6:1). The example low pressure turbine 46 provides the driving power to rotate fan section 22 and therefore the relationship between the number of turbine rotors in low pressure turbine 46 and number of blades 42 in fan section 22 disclose an example gas turbine engine 20 with increased power transfer efficiency.
- FIG. 2 is a schematic perspective view of one embodiment of the mid-turbine frame 57.
- the schematic view shown in Figure 2 is high level conceptual view and is intended to illustrate relative positioning of various components, but not actual shape of various components.
- the mid-turbine frame 57 includes an outer frame case 62, an inner frame case 64, and a plurality of hollow spokes 65.
- the outer frame case 62 includes an outer diameter surface 66.
- the inner frame case 64 includes an outer diameter surface 70 and an inner diameter surface 72.
- six hollow spokes 65 are distributed around the circumference of the inner frame case 64 to provide structural support between the inner frame case 64 and the outer frame case 62.
- the mid-turbine frame 57 can have more or less than six hollow spokes.
- the inner frame case 64 supports the rotor assembly via the bearing assemblies 38 (shown in Figure 1 ), and distributes the force from the inner frame case 64 to the outer frame case 62 via the plurality of hollow spokes 65. Attachment of the hollow spokes 65 to the outer frame case 62 is provided at a plurality of bosses 75 located circumferentially around the outer diameter surface 66 of the outer frame case 62.
- attachment of the hollow spokes 65 at the plurality of bosses 75 may be secured by a retaining nut 106 (shown in Figure 3 ) that allows the hollow spokes 65 to be tensioned.
- the hollow spokes 65 can be tensioned via a threaded connection so as to remain in tension during substantially all operating conditions of gas turbine engine 20.
- Apertures 76 formed in each of the plurality of bosses 75 allow cooling airflow to be distributed into a hollow portion of each of the hollow spokes 65. In this way, the cooling airflow is directed from the outer diameter through the hollow portions of the cooled hollow spokes 65 towards the inner frame case 64.
- the cooling airflow can function to cool the hollow spokes 65 and also to cool components radially inward of the inner frame case 64, such as the bearings 38.
- the cooling airflow is then directed to the low-rotor cavity 126 to cool the turbine rotors.
- Figure 3 is a cross-sectional view of the mid-turbine frame 57 taken along line 3-3 of Figure 2 .
- a hollow spoke 65A is one example of the hollow spokes 65 shown in Figure 2 .
- the hollow spoke 65A extends from the outer frame case 62 through the airfoil 59 to the inner frame case 64.
- the airfoil 59 extends from an outer platform 78 to an inner platform 80.
- the airfoil 59, the outer platform 78, and the inner platform 80 are integrally formed, and are all positioned radially inward of the outer frame case 62 and radially outward of the inner frame case 64.
- the airfoil 59, the outer platform 78, and the inner platform 80 define a portion of the core flow path C at the mid-turbine frame 57.
- the airfoil 59 extends axially from a leading edge 82 to a trailing edge 84.
- the airfoil 59 is oblong so as to be longer in the axial direction than in the circumferential direction.
- the airfoil 59 has a hollow interior 86, which is also relatively narrow in a chordal direction.
- the hollow spoke 65A includes a tie rod 90A and a retaining nut 92.
- the tie rod 90A is an elongated hollow tube that includes a threaded surface 94 at a radially outer end and a flange 96 at a radially inner end.
- the threaded surface 94 is on an outer surface 98 of the tie rod 90A.
- An inner passage surface 100 of the tie rod 90A defines an inlet passage 118 through the tie rod 90A.
- the tie rod 90A tapers along its length from the flange 96 at its radially inner end to the threaded surface 94 at its radially outer end.
- the retaining nut 92 includes a threaded surface 102 at a radially inner end of the retaining nut 92 and a flange 104 at a radially outer end of the retaining nut 92.
- the threaded surface 102 is on an inner surface 106 of the retaining nut 92.
- the flange 104 extends outward from an outer surface 108 of the retaining nut 92.
- the flange 96 of the tie rod 90A abuts against the inner frame case 64 so that the inner passage surface 100 aligns with a hole 110A in the inner frame case 64.
- the flange 96 is attached to the inner frame case 64 via bolts 112.
- the retaining nut 92 extends through a hole 114 in the outer frame case 62 such that the flange 104 abuts against the outer diameter surface 66 of the outer frame case 62.
- the flange 104 is attached to the outer frame case 62 via a bolt 116.
- the bolt 116 extends through the flange 104 into the outer frame case 62.
- the tie rod 90A is threaded into the retaining nut 92 to attach the tie rod 90A to the retaining nut 92.
- a portion but not all of the threaded surface 94 overlaps with a portion but not all of the threaded surface 102.
- the tie rod 90A is inserted through the hollow interior 86 of the airfoil 59 in a direction from radially inward to radially outward.
- the inner frame case 64 is then positioned radially inward of the tie rod 90A and attached to the tie rod 90A by the bolts 112.
- the retaining nut 92 is then inserted through the hole 114 and threadedly engaged with the tie rod 90A.
- the retaining nut 92 can be tightened, as desired, in a manner described below.
- the bolt 116 is inserted to fix the retaining nut 92 to the outer frame case 62 to prevent the retaining nut 92 from rotating and loosening.
- the threaded connection between the retaining nut 92 and the tie rod 90A is variable.
- the retaining nut 92 does not bottom out at any particular point when threaded on the tie rod 90A. This allows the retaining nut 92 to be threaded on the tie rod 90A to an extent determined during assembly, not predetermined prior to assembly. This allows the hollow spoke 65A, and the mid-turbine frame 57 in general, to be relatively insensitive to manufacturing tolerances.
- the inlet passage 118 branches off between a first branch 120 extending into a bearing support cavity 122 and a second branch 124 extending into a low rotor cavity 126.
- the first branch 120 extends in a radially inward direction through the inner frame case 64.
- a plug 128 is aligned with the first branch 120 and is located in an opening 130 in the hollow spoke 65A adjacent the outer diameter surface 70 of the inner frame case 64.
- the plug 128 includes an opening 129 having a conical radially outer portion that tapers to a cylindrical channel on a radially inner side.
- the cylindrical channel of the plug 128 includes a diameter D1 that is smaller than a diameter D2 defined by the inner passage surface 100.
- the plug 128 includes a diameter D1, however, the diameter D1 could be any dimension that is smaller than the dimension D2 in order to control the amount of cooling airflow that travels into the bearing support cavity 122.
- the plug 128 is shown contacting the hollow spoke 65A and the inner frame case 64, the plug 128 could be located anywhere within the first branch 120.
- the plug 128 could be solid and prevent the cooling airflow from entering the bearing support cavity 122 so the entire cooling airflow must travel through the second branch 124.
- the opening 130 in the tie rod 90A could be reduced to the diameter D1 so that the plug 128 could be eliminated.
- the second branch 124 extends in an axially downstream direction perpendicular to the first branch 120. Although the second branch 124 is shown being perpendicular to the first branch 120, the second branch 124 could be within 30 degrees of being perpendicular to the first branch 120.
- the second branch 124 is in fluid communication with the low rotor cavity through to a fitting 132 that extends through the inner frame case 64 and connects to a swirler tube 142.
- the fitting 132 includes a transfer tube 134 pressed, welded, or brazed into an opening 138 in the hollow spoke 65A on a first end and engages a cup boss 136 on a second end.
- the transfer tube 134 could also be an integral part of the cup boss 136.
- a piston ring creates a seal between an outer diameter of the transfer tube 134 and the cup boss 136.
- the cup boss 136 is fastened to the inner frame case 64 with fasteners 140 and is aligned with a hole 110B in the inner frame case 64.
- the fasteners 140 also secure the swirler tube 142 to an opposite side of the inner frame case 64 from the cup boss 136.
- the swirler tube 142 directs the cooling airflow into the low rotor cavity in the direction of rotation of the low rotor to reduce turning and aerodynamic losses in the cooling airflow. By pre-swirling the cooling air flow prior to entering the low-rotor cavity 126, the heat up of the cooling air flow is reduced which lowers a temperature of the low-rotor cavity.
- a restricting ring 144 is located between the swirler tube 142 and the inner diameter surface 72.
- the restricting ring 144 includes a diameter D3 which is smaller than a diameter D4 of the second branch 124.
- the restricting ring 144 restricts the amount of cooling airflow through the second branch 124 to aid in dividing the amount of cooling airflow traveling into the bearing support cavity 122 and the low-rotor cavity 126.
- the restricting ring 144 is shown between the swirler tube 142 and the inner frame case 64, the restricting ring 144 could be located anywhere within the second branch 124 to reduce the cooling airflow into the low-rotor cavity 126.
- a portion of the second branch 124 may include a portion with a reduced diameter, such as reducing a diameter of the second branch 124 extending through the transfer tube 134, the boss 136, or the hole 110B to meter the cooling airflow.
- the a first portion of cooling airflow travels into the bearing support cavity 122 and a second portion of cooling airflow travels into the low-rotor cavity 126, with the second portion being greater than the first portion.
- a cavity connecting opening 146 is located between the bearing support cavity 122 and the low-rotor cavity 126.
- the cavity connecting opening 146 may be removed or blocked to fluidly separate the bearing support cavity 122 from the low-rotor cavity 126. Separating the bearing support cavity 122 from the low-rotor cavity 126 can prevent cooling airflow mixed with oil in the bearing support cavity 122 from entering the low-rotor cavity 126.
- FIG. 6 illustrates another example tie rod 90A'.
- the tie rod 90A' is similar to the tie rod 90A except where described below or shown in the Figures.
- An inner passage surface 100' defines an inlet passage 118' and extends radially inward and branches off to a second branch 124' extending into the low rotor cavity 126.
- the second branch 124' extends in an axially downstream direction perpendicular to the inlet passage 118'. Although the second branch 124' is shown being perpendicular to the inlet passage 118', the second branch 124' could be within 30 degrees of being perpendicular to the inlet branch 118'.
- the second branch 124' is in fluid communication with the low rotor cavity 126 through to the fitting 132 which extends through the inner frame case 64 and connects to the swirler tube 142.
- FIGs 7A and 7B illustrate the swirler tube 142 attached to the inner frame case 64.
- the swirler tube 142 includes a nozzle 150 and a flange 152 directly contacting the inner frame case 64.
- the flange 152 includes a pair of fastener openings 162 for accepting the fasteners 140.
- the nozzle 150 includes a base portion 154 attached to the flange 152 and an end portion 158 spaced from the flange on a distal end of the nozzle 150.
- An inlet 156 to the nozzle 150 is defined by the base portion 154 of the nozzle 150 and extends perpendicular to the flange 152 and the inner frame case 64. In the illustrated example, the inlet 156 has circular cross section. ( Figure 7C ). However, the inlet 156 could be elliptical, racetrack, or another shape.
- the swirler tube 142 could be welded, brazed, or riveted to the inner frame case 64 or integrally cast as part of the inner frame case 64.
- the end portion 158 is located at a distal end of the nozzle 150 and defines an outlet 160.
- the outlet 160 includes a race track cross section with curved ends 160a spaced from each other by parallel portions 160b. ( Figure 7D ).
- the outlet 160 could include an elliptical cross section.
- the nozzle 150 turns the cooling airflow in the low-rotor cavity 126 in the direction of rotation of the low pressure turbine 46 and diffuses the cooling airflow as the cooling airflow travels through the nozzle 150.
- the nozzle 150 diffuses the cooling airflow because the inlet 156 includes a cross-sectional area that is smaller than the cross-sectional area of the outlet 160.
- the diffused cooling airflow results in a lower exit loss when the cooling airflow enters the slower rotational flow field of the low-rotor cavity 126.
- the swirler tube 142 could be manufactured by casting-machining, fully machining, fabricated machining with welding, or direct metal laser sinter.
- FIGS 8A and 8B illustrate another example swirler tube 242.
- the swirler tube 242 is similar to the swirler tube 142 except where described below or shown in the Figures.
- the swirler tube 242 includes a nozzle 250 and a flange 252 directly contacting the inner frame case 64.
- the flange 252 includes a pair of fastener openings 262 for accepting the fasteners 140.
- the nozzle 250 includes a base portion 254 attached to the flange 252 and an end portion 258.
- the nozzle 250 includes a circular cross-section along a length of the nozzle 250. However, the nozzle 250 could include an elliptical, race track, or other cross-sectional shape.
- an outlet 260 of the nozzle 250 is directed circumferentially at an angle ⁇ relative to the radial direction.
- the nozzle 250 extends axially downstream and radially inward at an angle ⁇ .
- the angle ⁇ is approximately 70 degrees and the angle ⁇ is approximately 20.6 degrees.
- the angle ⁇ is between approximately 50 and 80 degrees and the angle ⁇ is between approximately 15 and 45 degrees
- FIG 8C illustrates another example swirler tube 242'.
- the swirler tube 242' is similar to the swirler tube 242 except where described below or shown in the Figures.
- a base portion 254' of a nozzle 250' is integral with a flange 252'.
- the base portion 254' includes an opening 262' for accepting an elbow 264' to direct the cooling airflow in the same direction as the nozzle 250.
- the elbow 264' is brazed or welded to the base portion 254'.
- FIGS 9A-9C illustrate yet another example swirler tube 342.
- the swirler tube 342 is similar to the swirler tube 142 except where described below or shown in the Figures.
- the swirler tube 342 includes a nozzle 350 and a flange 352 with fastener openings 362 for accepting fasteners 140.
- the nozzle 350 includes a base portion 354 attached to the flange 352 and an end portion 358.
- the nozzle 350 includes a circular cross section.
- the nozzle 350 could include an elliptical cross section, race track cross section, and/or a cross section of increasing area.
- An outlet 360 of the nozzle 350 is angled at an angle ⁇ relative to radial direction as shown in Figure 9C .
- the angle ⁇ is approximately 78 degrees. In another example, the angle ⁇ is between approximately 75 and 85 degrees.
- the outlet 360 does not extend in a circumferential direction and swirl the flow in the circumferential direction.
- the flange 352 includes a middle portion 370 having a first thickness and a pair of outer portions 372 having a second thickness that is less than the first thickness.
- An anti-rotation lip 374 is located at an intersection of the middle portion 370 and the pair of outer portions 372. The anti-rotation lip 374 engages an edge 376 on a fastener plate 378 ( Figure 9D ) to prevent rotation a head of the fastener 140.
- FIGS 10A and 10B illustrate a further example swirler tube 442.
- the swirler tube 442 is similar to the swirler tube 342 except where described below or shown in the Figures.
- the swirler tube 442 includes a nozzle 450 attached to a flange 452 with fastener openings 362 for accepting fasteners 140.
- the nozzle 450 includes a base portion 454 and an end portion 458.
- the nozzle 450 includes a circular cross section.
- the nozzle 450 could include an elliptical cross section, race track cross section, and/or a cross section of increasing area.
- An outlet 460 of the nozzle 450 is angled at an angle ⁇ relative to radial direction as shown in Figure 10B .
- the angle ⁇ is approximately 78 degrees.
- the outlet 360 does not extend in a circumferential direction.
- the angle ⁇ is between approximately 75 and 85 degrees.
- FIGS 11A-11C illustrate a further example swirler tube 542.
- the swirler tube 542 is similar to the swirler tube 142 except where described below or shown in the Figures.
- the swirler tube 542 includes a nozzle 550 and a flange 552 with fastener openings 562 for accepting fasteners 140.
- the nozzle 550 includes a base portion 554 attached to the flange 552 and an end portion 558.
- the nozzle 550 includes a circular cross section.
- the nozzle 550 could include an elliptical cross section, race track cross section, and/or a cross section of increasing area.
- an outlet 560 of the nozzle 550 is directed circumferentially inward at an angle ⁇ relative to the radial direction.
- the nozzle 550 extends axially downstream and radially inward at an angle ⁇ .
- the angle ⁇ is approximately 70 degrees and the angle ⁇ is approximately 20.6 degrees.
- the flange 552 includes a middle portion 570 having a first thickness and a pair of outer portions 572 having a second thickness that is less than the first thickness.
- An anti-rotation lip 574 is located at an intersection of the middle portion 570 and the pair of outer portions 572. The anti-rotation lip 574 engages an edge 576 on a fastener plate 578 ( Figure 9D ) to prevent rotation of a head of the fastener 140.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- The present disclosure relates generally to a gas turbine engine, and in particular to a mid-turbine frame (MTF) included in a gas turbine engine.
- A gas turbine engine typically includes a fan section, a compressor section, a combustor section, and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section.
- A mid-turbine frame (MTF) is positioned between a high pressure turbine stage and a low pressure turbine stage of a gas turbine engine. The MTF supports one or more bearings and transfers bearing loads from an inner portion of the gas turbine engine to an outer engine frame. The MTF also serves to route air from the high pressure turbine stage to the low pressure turbine stage.
- A prior art gas turbine engine and method of cooling a portion of the same having the features of the preamble to claims 1 and 9 is disclosed in
US 2013/219919 . - From one aspect, the present invention provides a gas turbine engine in accordance with claim 1.
- In an embodiment of the above, the swirler tube extends in a circumferential direction.
- In a further embodiment of any of the above, the circumferential direction is directed at between 50 and 80 degrees relative to a radial direction.
- In a further embodiment of any of the above, the swirler tube is directed radially inward at an angle between 15 and 45 degrees.
- In a further embodiment of any of the above, the swirler tube includes an outlet directed radially inward at an angle between 75 and 85 degrees to a radial direction.
- In a further embodiment of any of the above, the swirler tube includes an inlet having a first cross sectional area and an out let having a second cross-sectional area. The second cross-sectional area is larger than the first cross-sectional area.
- In a further embodiment of any of the above, a restricting ring is located in at least one branch.
- In a further embodiment of any of the above, at least one branch extends in the axial direction and includes a portion with a reduced diameter for metering the cooling airflow through at least one branch.
- From another aspect, the present invention provides a method in accordance with claim 9.
- In an embodiment of the above, the method includes directing the cooling airflow in a circumferential direction.
- In a further embodiment of any of the above, the swirler tube includes an inlet having a first cross sectional area and an out let having a second cross sectional area with the second cross sectional area being larger than the first cross sectional area.
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Figure 1 is a schematic view of an example gas turbine engine. -
Figure 2 is a schematic perspective view of an example mid-turbine frame in the gas turbine engine. -
Figure 3 is a sectional view taken along line 3-3 ofFigure 2 . -
Figure 4 is a perspective sectional view of an example hollow spoke. -
Figure 5 is a perspective view of the hollow spoke. -
Figure 6 illustrates another example mid-turbine frame. -
Figure 7A and 7B illustrate a perspective view of an example swirler tube. -
Figure 7C illustrates a section view alongline 7C-7C ofFigure 7B . -
Figure 7D is an end view of the example swirler tube. -
Figures 8A and8C illustrate another example swirler tube. -
Figure 8B illustrates a section view alongline 8B-8B inFigure 8A . -
Figure 9A illustrates an end view of yet another example swirler tube. -
Figure 9B illustrates a perspective view of the swirler tube ofFigure 9A . -
Figure 9C illustrates a side view of the swirler tube ofFigure 9A . -
Figure 9D illustrates an example fastener plate. -
Figure 10A illustrates an end view of a further example swirler tube. -
Figure 10B illustrates a section view alongline 10B-10B ofFigure 10A . -
Figure 11A illustrates a perspective view of still a further example swirler tube. -
Figure 11B illustrates a side view of the swirler tube ofFigure 11A . -
Figure 11C illustrates an end view of the swirler tube ofFigure 11A . -
Figure 1 schematically illustrates agas turbine engine 20. Thegas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates afan section 22, acompressor section 24, acombustor section 26 and aturbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. Thefan section 22 drives air along a bypass flow path B in a bypass duct defined within anacelle 15, while thecompressor section 24 drives air along a core flow path C for compression and communication into thecombustor section 26 then expansion through theturbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. - The
exemplary engine 20 generally includes alow speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing systems 38. It should be understood thatvarious bearing systems 38 at various locations may alternatively or additionally be provided, and the location ofbearing systems 38 may be varied as appropriate to the application. - The
low speed spool 30 generally includes aninner shaft 40 that interconnects afan 42, a first (or low)pressure compressor 44 and a first (or low)pressure turbine 46. Theinner shaft 40 is connected to thefan 42 through a speed change mechanism, which in exemplarygas turbine engine 20 is illustrated as a gearedarchitecture 48 to drive thefan 42 at a lower speed than thelow speed spool 30. Thehigh speed spool 32 includes anouter shaft 50 that interconnects a second (or high)pressure compressor 52 and a second (or high)pressure turbine 54. Acombustor 56 is arranged inexemplary gas turbine 20 between thehigh pressure compressor 52 and thehigh pressure turbine 54. Amid-turbine frame 57 of the enginestatic structure 36 is arranged generally between thehigh pressure turbine 54 and thelow pressure turbine 46. Themid-turbine frame 57 further supports bearingsystems 38 in theturbine section 28. Theinner shaft 40 and theouter shaft 50 are concentric and rotate viabearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes. - The core airflow is compressed by the
low pressure compressor 44 then thehigh pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over thehigh pressure turbine 54 andlow pressure turbine 46. Themid-turbine frame 57 includesairfoils 59 which are in the core airflow path C. Theturbines low speed spool 30 andhigh speed spool 32 in response to the expansion. It will be appreciated that each of the positions of thefan section 22,compressor section 24,combustor section 26,turbine section 28, and fandrive gear system 48 may be varied. For example,gear system 48 may be located aft ofcombustor section 26 or even aft ofturbine section 28, andfan section 22 may be positioned forward or aft of the location ofgear system 48. - The
engine 20 in one example is a high-bypass geared aircraft engine. In a further example, theengine 20 bypass ratio is greater than about six (6:1), with an example embodiment being greater than about ten (10:1), the gearedarchitecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 (2.3:1) and thelow pressure turbine 46 has a pressure ratio that is greater than about five. In one disclosed embodiment, theengine 20 bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of thelow pressure compressor 44, and thelow pressure turbine 46 has a pressure ratio that is greater than about five (5:1).Low pressure turbine 46 pressure ratio is pressure measured prior to inlet oflow pressure turbine 46 as related to the pressure at the outlet of thelow pressure turbine 46 prior to an exhaust nozzle. The gearedarchitecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 (2.3:1). It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans. - A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The
fan section 22 of theengine 20 is designed for a particular flight condition -- typically cruise at about 0.8 Mach (274 m/s) and about 35,000 feet (10,668 m). The flight condition of 0.8 Mach (274 m/s) and 35,000 ft (10,668 meters), with the engine at its best fuel consumption - also known as "bucket cruise Thrust Specific Fuel Consumption ('TSFC')" - is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. "Low fan pressure ratio" is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane ("FEGV") system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45 (1.45:1). "Low corrected fan tip speed" is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram °R) / (518.7 °R)]0.5. The "Low corrected fan tip speed" as disclosed herein according to one non-limiting embodiment is less than about 1150 ft / second (350.5 meters/second). - The example gas turbine engine includes
fan 42 that comprises in one non-limiting embodiment less than about 26 fan blades. In another non-limiting embodiment,fan section 22 includes less than about 20 fan blades. Moreover, in one disclosed embodimentlow pressure turbine 46 includes no more than about 6 turbine rotors. In another non-limiting example embodimentlow pressure turbine 46 includes about 3 turbine rotors. A ratio between number offan blades 42 and the number of low pressure turbine rotors is between about 3.3 and about 8.6 (about 3.3:1 and about 8.6:1). The examplelow pressure turbine 46 provides the driving power to rotatefan section 22 and therefore the relationship between the number of turbine rotors inlow pressure turbine 46 and number ofblades 42 infan section 22 disclose an examplegas turbine engine 20 with increased power transfer efficiency. -
Figure 2 is a schematic perspective view of one embodiment of themid-turbine frame 57. The schematic view shown inFigure 2 is high level conceptual view and is intended to illustrate relative positioning of various components, but not actual shape of various components. Themid-turbine frame 57 includes anouter frame case 62, aninner frame case 64, and a plurality ofhollow spokes 65. Theouter frame case 62 includes anouter diameter surface 66. Theinner frame case 64 includes anouter diameter surface 70 and aninner diameter surface 72. In the embodiment shown inFigure 2 , sixhollow spokes 65 are distributed around the circumference of theinner frame case 64 to provide structural support between theinner frame case 64 and theouter frame case 62. In alternative embodiments, themid-turbine frame 57 can have more or less than six hollow spokes. - The
inner frame case 64 supports the rotor assembly via the bearing assemblies 38 (shown inFigure 1 ), and distributes the force from theinner frame case 64 to theouter frame case 62 via the plurality ofhollow spokes 65. Attachment of thehollow spokes 65 to theouter frame case 62 is provided at a plurality ofbosses 75 located circumferentially around theouter diameter surface 66 of theouter frame case 62. - In one embodiment, attachment of the
hollow spokes 65 at the plurality ofbosses 75 may be secured by a retaining nut 106 (shown inFigure 3 ) that allows thehollow spokes 65 to be tensioned. Thehollow spokes 65 can be tensioned via a threaded connection so as to remain in tension during substantially all operating conditions ofgas turbine engine 20.Apertures 76 formed in each of the plurality ofbosses 75 allow cooling airflow to be distributed into a hollow portion of each of thehollow spokes 65. In this way, the cooling airflow is directed from the outer diameter through the hollow portions of the cooledhollow spokes 65 towards theinner frame case 64. The cooling airflow can function to cool thehollow spokes 65 and also to cool components radially inward of theinner frame case 64, such as thebearings 38. The cooling airflow is then directed to the low-rotor cavity 126 to cool the turbine rotors. -
Figure 3 is a cross-sectional view of themid-turbine frame 57 taken along line 3-3 ofFigure 2 . Ahollow spoke 65A is one example of thehollow spokes 65 shown inFigure 2 . The hollow spoke 65A extends from theouter frame case 62 through theairfoil 59 to theinner frame case 64. Theairfoil 59 extends from anouter platform 78 to aninner platform 80. In the illustrated embodiment, theairfoil 59, theouter platform 78, and theinner platform 80 are integrally formed, and are all positioned radially inward of theouter frame case 62 and radially outward of theinner frame case 64. Theairfoil 59, theouter platform 78, and theinner platform 80 define a portion of the core flow path C at themid-turbine frame 57. Theairfoil 59 extends axially from a leadingedge 82 to a trailingedge 84. Theairfoil 59 is oblong so as to be longer in the axial direction than in the circumferential direction. Theairfoil 59 has ahollow interior 86, which is also relatively narrow in a chordal direction. - In the illustrated embodiment, the hollow spoke 65A includes a
tie rod 90A and a retainingnut 92. Thetie rod 90A is an elongated hollow tube that includes a threadedsurface 94 at a radially outer end and aflange 96 at a radially inner end. The threadedsurface 94 is on anouter surface 98 of thetie rod 90A. Aninner passage surface 100 of thetie rod 90A defines aninlet passage 118 through thetie rod 90A. Thetie rod 90A tapers along its length from theflange 96 at its radially inner end to the threadedsurface 94 at its radially outer end. - The retaining
nut 92 includes a threadedsurface 102 at a radially inner end of the retainingnut 92 and a flange 104 at a radially outer end of the retainingnut 92. The threadedsurface 102 is on aninner surface 106 of the retainingnut 92. The flange 104 extends outward from anouter surface 108 of the retainingnut 92. - In the illustrated embodiment, the
flange 96 of thetie rod 90A abuts against theinner frame case 64 so that theinner passage surface 100 aligns with ahole 110A in theinner frame case 64. Theflange 96 is attached to theinner frame case 64 viabolts 112. The retainingnut 92 extends through a hole 114 in theouter frame case 62 such that the flange 104 abuts against theouter diameter surface 66 of theouter frame case 62. The flange 104 is attached to theouter frame case 62 via abolt 116. Thebolt 116 extends through the flange 104 into theouter frame case 62. Thetie rod 90A is threaded into the retainingnut 92 to attach thetie rod 90A to the retainingnut 92. In the illustrated embodiment, a portion but not all of the threadedsurface 94 overlaps with a portion but not all of the threadedsurface 102. - During assembly, the
tie rod 90A is inserted through thehollow interior 86 of theairfoil 59 in a direction from radially inward to radially outward. Theinner frame case 64 is then positioned radially inward of thetie rod 90A and attached to thetie rod 90A by thebolts 112. The retainingnut 92 is then inserted through the hole 114 and threadedly engaged with thetie rod 90A. The retainingnut 92 can be tightened, as desired, in a manner described below. Once the retainingnut 92 is suitably tightened on thetie rod 90A, thebolt 116 is inserted to fix the retainingnut 92 to theouter frame case 62 to prevent the retainingnut 92 from rotating and loosening. - Because the threaded
surface 94 overlaps with the threadedsurface 102 only partially, the threaded connection between the retainingnut 92 and thetie rod 90A is variable. The retainingnut 92 does not bottom out at any particular point when threaded on thetie rod 90A. This allows the retainingnut 92 to be threaded on thetie rod 90A to an extent determined during assembly, not predetermined prior to assembly. This allows the hollow spoke 65A, and themid-turbine frame 57 in general, to be relatively insensitive to manufacturing tolerances. - The
inlet passage 118 branches off between afirst branch 120 extending into abearing support cavity 122 and asecond branch 124 extending into alow rotor cavity 126. Thefirst branch 120 extends in a radially inward direction through theinner frame case 64. - A
plug 128 is aligned with thefirst branch 120 and is located in anopening 130 in the hollow spoke 65A adjacent theouter diameter surface 70 of theinner frame case 64. Theplug 128 includes anopening 129 having a conical radially outer portion that tapers to a cylindrical channel on a radially inner side. The cylindrical channel of theplug 128 includes a diameter D1 that is smaller than a diameter D2 defined by theinner passage surface 100. In the illustrated example, theplug 128 includes a diameter D1, however, the diameter D1 could be any dimension that is smaller than the dimension D2 in order to control the amount of cooling airflow that travels into thebearing support cavity 122. Although theplug 128 is shown contacting the hollow spoke 65A and theinner frame case 64, theplug 128 could be located anywhere within thefirst branch 120. - Alternatively, the
plug 128 could be solid and prevent the cooling airflow from entering thebearing support cavity 122 so the entire cooling airflow must travel through thesecond branch 124. In yet another example embodiment, theopening 130 in thetie rod 90A could be reduced to the diameter D1 so that theplug 128 could be eliminated. - The
second branch 124 extends in an axially downstream direction perpendicular to thefirst branch 120. Although thesecond branch 124 is shown being perpendicular to thefirst branch 120, thesecond branch 124 could be within 30 degrees of being perpendicular to thefirst branch 120. Thesecond branch 124 is in fluid communication with the low rotor cavity through to a fitting 132 that extends through theinner frame case 64 and connects to aswirler tube 142. - The fitting 132 includes a
transfer tube 134 pressed, welded, or brazed into anopening 138 in the hollow spoke 65A on a first end and engages acup boss 136 on a second end. Thetransfer tube 134 could also be an integral part of thecup boss 136. A piston ring creates a seal between an outer diameter of thetransfer tube 134 and thecup boss 136. As shown inFigures 4 and 5 , thecup boss 136 is fastened to theinner frame case 64 withfasteners 140 and is aligned with ahole 110B in theinner frame case 64. Thefasteners 140 also secure theswirler tube 142 to an opposite side of theinner frame case 64 from thecup boss 136. Theswirler tube 142 directs the cooling airflow into the low rotor cavity in the direction of rotation of the low rotor to reduce turning and aerodynamic losses in the cooling airflow. By pre-swirling the cooling air flow prior to entering the low-rotor cavity 126, the heat up of the cooling air flow is reduced which lowers a temperature of the low-rotor cavity. - A restricting
ring 144 is located between theswirler tube 142 and theinner diameter surface 72. The restrictingring 144 includes a diameter D3 which is smaller than a diameter D4 of thesecond branch 124. The restrictingring 144 restricts the amount of cooling airflow through thesecond branch 124 to aid in dividing the amount of cooling airflow traveling into thebearing support cavity 122 and the low-rotor cavity 126. Although the restrictingring 144 is shown between theswirler tube 142 and theinner frame case 64, the restrictingring 144 could be located anywhere within thesecond branch 124 to reduce the cooling airflow into the low-rotor cavity 126. Alternatively, or in addition to the restrictingring 144, a portion of thesecond branch 124 may include a portion with a reduced diameter, such as reducing a diameter of thesecond branch 124 extending through thetransfer tube 134, theboss 136, or thehole 110B to meter the cooling airflow. - In one example, the a first portion of cooling airflow travels into the
bearing support cavity 122 and a second portion of cooling airflow travels into the low-rotor cavity 126, with the second portion being greater than the first portion. - In the illustrated example, a
cavity connecting opening 146 is located between the bearingsupport cavity 122 and the low-rotor cavity 126. Thecavity connecting opening 146 may be removed or blocked to fluidly separate thebearing support cavity 122 from the low-rotor cavity 126. Separating thebearing support cavity 122 from the low-rotor cavity 126 can prevent cooling airflow mixed with oil in thebearing support cavity 122 from entering the low-rotor cavity 126. -
Figure 6 illustrates anotherexample tie rod 90A'. Thetie rod 90A' is similar to thetie rod 90A except where described below or shown in the Figures. An inner passage surface 100' defines an inlet passage 118' and extends radially inward and branches off to a second branch 124' extending into thelow rotor cavity 126. - The second branch 124' extends in an axially downstream direction perpendicular to the inlet passage 118'. Although the second branch 124' is shown being perpendicular to the inlet passage 118', the second branch 124' could be within 30 degrees of being perpendicular to the inlet branch 118'. The second branch 124' is in fluid communication with the
low rotor cavity 126 through to the fitting 132 which extends through theinner frame case 64 and connects to theswirler tube 142. -
Figures 7A and 7B illustrate theswirler tube 142 attached to theinner frame case 64. Theswirler tube 142 includes anozzle 150 and aflange 152 directly contacting theinner frame case 64. Theflange 152 includes a pair offastener openings 162 for accepting thefasteners 140. Thenozzle 150 includes abase portion 154 attached to theflange 152 and anend portion 158 spaced from the flange on a distal end of thenozzle 150. Aninlet 156 to thenozzle 150 is defined by thebase portion 154 of thenozzle 150 and extends perpendicular to theflange 152 and theinner frame case 64. In the illustrated example, theinlet 156 has circular cross section. (Figure 7C ). However, theinlet 156 could be elliptical, racetrack, or another shape. - In an alternate embodiment, the
swirler tube 142 could be welded, brazed, or riveted to theinner frame case 64 or integrally cast as part of theinner frame case 64. - The
end portion 158 is located at a distal end of thenozzle 150 and defines anoutlet 160. In the illustrated example, theoutlet 160 includes a race track cross section withcurved ends 160a spaced from each other byparallel portions 160b. (Figure 7D ). Alternatively, theoutlet 160 could include an elliptical cross section. - The
nozzle 150 turns the cooling airflow in the low-rotor cavity 126 in the direction of rotation of thelow pressure turbine 46 and diffuses the cooling airflow as the cooling airflow travels through thenozzle 150. Thenozzle 150 diffuses the cooling airflow because theinlet 156 includes a cross-sectional area that is smaller than the cross-sectional area of theoutlet 160. The diffused cooling airflow results in a lower exit loss when the cooling airflow enters the slower rotational flow field of the low-rotor cavity 126. - The
swirler tube 142 could be manufactured by casting-machining, fully machining, fabricated machining with welding, or direct metal laser sinter. -
Figures 8A and 8B illustrate anotherexample swirler tube 242. Theswirler tube 242 is similar to theswirler tube 142 except where described below or shown in the Figures. Theswirler tube 242 includes anozzle 250 and aflange 252 directly contacting theinner frame case 64. Theflange 252 includes a pair offastener openings 262 for accepting thefasteners 140. Thenozzle 250 includes abase portion 254 attached to theflange 252 and anend portion 258. Thenozzle 250 includes a circular cross-section along a length of thenozzle 250. However, thenozzle 250 could include an elliptical, race track, or other cross-sectional shape. - As shown in
Figure 8A , anoutlet 260 of thenozzle 250 is directed circumferentially at an angle α relative to the radial direction. As shown inFigure 8B , thenozzle 250 extends axially downstream and radially inward at an angle β. In the illustrated example, the angle α is approximately 70 degrees and the angle β is approximately 20.6 degrees. In another example, the angle α is between approximately 50 and 80 degrees and the angle β is between approximately 15 and 45 degrees -
Figure 8C illustrates another example swirler tube 242'. The swirler tube 242' is similar to theswirler tube 242 except where described below or shown in the Figures. A base portion 254' of a nozzle 250' is integral with a flange 252'. The base portion 254' includes an opening 262' for accepting an elbow 264' to direct the cooling airflow in the same direction as thenozzle 250. The elbow 264' is brazed or welded to the base portion 254'. -
Figures 9A-9C illustrate yet anotherexample swirler tube 342. Theswirler tube 342 is similar to theswirler tube 142 except where described below or shown in the Figures. Theswirler tube 342 includes anozzle 350 and aflange 352 withfastener openings 362 for acceptingfasteners 140. Thenozzle 350 includes abase portion 354 attached to theflange 352 and anend portion 358. In the illustrated example, thenozzle 350 includes a circular cross section. In another example, thenozzle 350 could include an elliptical cross section, race track cross section, and/or a cross section of increasing area. - An
outlet 360 of thenozzle 350 is angled at an angle δ relative to radial direction as shown inFigure 9C . In the illustrated example, the angle δ is approximately 78 degrees. In another example, the angle δ is between approximately 75 and 85 degrees. Theoutlet 360 does not extend in a circumferential direction and swirl the flow in the circumferential direction. - As shown in
Figures 9A-9C , theflange 352 includes amiddle portion 370 having a first thickness and a pair ofouter portions 372 having a second thickness that is less than the first thickness. Ananti-rotation lip 374 is located at an intersection of themiddle portion 370 and the pair ofouter portions 372. Theanti-rotation lip 374 engages anedge 376 on a fastener plate 378 (Figure 9D ) to prevent rotation a head of thefastener 140. -
Figures 10A and 10B illustrate a furtherexample swirler tube 442. Theswirler tube 442 is similar to theswirler tube 342 except where described below or shown in the Figures. Theswirler tube 442 includes anozzle 450 attached to aflange 452 withfastener openings 362 for acceptingfasteners 140. Thenozzle 450 includes abase portion 454 and anend portion 458. In the illustrated example, thenozzle 450 includes a circular cross section. In another example, thenozzle 450 could include an elliptical cross section, race track cross section, and/or a cross section of increasing area. - An
outlet 460 of thenozzle 450 is angled at an angle δ relative to radial direction as shown inFigure 10B . In the illustrated example, the angle δ is approximately 78 degrees. Theoutlet 360 does not extend in a circumferential direction. In another example, the angle δ is between approximately 75 and 85 degrees. -
Figures 11A-11C illustrate a furtherexample swirler tube 542. Theswirler tube 542 is similar to theswirler tube 142 except where described below or shown in the Figures. Theswirler tube 542 includes anozzle 550 and aflange 552 withfastener openings 562 for acceptingfasteners 140. Thenozzle 550 includes abase portion 554 attached to theflange 552 and anend portion 558. In the illustrated example, thenozzle 550 includes a circular cross section. In another example, thenozzle 550 could include an elliptical cross section, race track cross section, and/or a cross section of increasing area. - As shown in
Figure 11C , anoutlet 560 of thenozzle 550 is directed circumferentially inward at an angle α relative to the radial direction. As shown inFigure 11B , thenozzle 550 extends axially downstream and radially inward at an angle β. In the illustrated example, the angle α is approximately 70 degrees and the angle β is approximately 20.6 degrees. - The
flange 552 includes amiddle portion 570 having a first thickness and a pair ofouter portions 572 having a second thickness that is less than the first thickness. Ananti-rotation lip 574 is located at an intersection of themiddle portion 570 and the pair ofouter portions 572. Theanti-rotation lip 574 engages an edge 576 on a fastener plate 578 (Figure 9D ) to prevent rotation of a head of thefastener 140. - It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed and illustrated in these exemplary embodiments, other arrangements could also benefit from the teachings of this disclosure.
- The foregoing description shall be interpreted as illustrative and not in any limiting sense. A worker of ordinary skill in the art would understand that certain modifications could come within the scope of the appended claims.
Claims (11)
- A gas turbine engine (20) comprising:a mid-turbine frame (57) located axially between a first turbine (54) and a second turbine (46), the mid-turbine frame (57) comprising:an outer frame case (62);an inner frame case (64) including a fluid passage;at least one spoke (65;65A) connecting the outer frame case (62) to the inner frame case (64), wherein the spoke (65;65A) includes an inlet passage (118;118') with at least one branch (124;124') extending in an axial direction in fluid communication with the fluid passage;a swirler tube (142;242;242';342;442;542) in fluid communication with the fluid passage and configured to direct cooling airflow in a radial inward and downstream direction,characterised by:
a fitting (132) extending through the inner frame case (64) and connecting the fluid passage to the swirler tube (142). - The gas turbine engine (20) of claim 1, wherein the swirler tube (142;...542) extends in a circumferential direction.
- The gas turbine engine (20) of claim 2, wherein the circumferential direction is directed at between 50 and 80 degrees relative to a radial direction.
- The gas turbine engine (20) of any preceding claim, wherein the swirler tube (142;...542) is directed radially inward at an angle between 15 and 45 degrees.
- The gas turbine engine (20) of claim 1 or 2, wherein the swirler tube (142;...542) includes an outlet (160;260;260';360;460) directed radially inward at an angle between 75 and 85 degrees to a radial direction.
- The gas turbine engine (20) of any preceding claim, wherein the swirler tube (142;...542) includes an inlet (156) having a first cross sectional area and an/the outlet (160;...460) having a second cross-sectional area with the second cross-sectional area being larger than the first cross-sectional area.
- The gas turbine engine (20) of any preceding claim, further comprising a restricting ring (144) located in the at least one branch (124;124').
- The gas turbine engine (20) of any preceding claim, wherein the at least one branch (124; 124') extending in the axial direction includes a portion with a reduced diameter (D4) for metering the cooling airflow through the at least one branch (124;124').
- A method of cooling a mid-turbine frame (57) located axially between a first turbine (54) and a second turbine (46) of a gas turbine engine (20), the method comprising:directing cooling airflow through a passage in an inner frame case (64); anddirecting the cooling airflow through a swirler tube (142; 242;242';342;442;542) toward a low pressure turbine rotor in a radially inward and downstream direction, wherein at least one spoke (65;65A) connects an outer frame case (62) to the inner frame case (64), and the spoke (65;65A) includes an inlet passage (118;118') with at least one branch (124;124') extending in an axial direction in fluid communication with a fluid passage in the inner frame case (64); andcharacterised in that:
a fitting (132) extends through the inner frame case (64) and connects the fluid passage to the swirler tube (142). - The method of claim 9, further comprising directing the cooling airflow in a circumferential direction.
- The method of claim 9 or 10, wherein the swirler tube (142;...542) includes an inlet (156) having a first cross sectional area and an outlet (160;...460) having a second cross sectional area with the second cross sectional area being larger than the first cross sectional area.
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US14/598,492 US9920651B2 (en) | 2015-01-16 | 2015-01-16 | Cooling passages for a mid-turbine frame |
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EP3045672B1 true EP3045672B1 (en) | 2021-09-22 |
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US9915170B2 (en) * | 2015-03-20 | 2018-03-13 | United Technologies Corporation | Cooling passages for a mid-turbine frame |
US10247035B2 (en) | 2015-07-24 | 2019-04-02 | Pratt & Whitney Canada Corp. | Spoke locking architecture |
CA2936180A1 (en) | 2015-07-24 | 2017-01-24 | Pratt & Whitney Canada Corp. | Multiple spoke cooling system and method |
US10443449B2 (en) | 2015-07-24 | 2019-10-15 | Pratt & Whitney Canada Corp. | Spoke mounting arrangement |
US10273812B2 (en) | 2015-12-18 | 2019-04-30 | Pratt & Whitney Canada Corp. | Turbine rotor coolant supply system |
GB2551777B (en) * | 2016-06-30 | 2018-09-12 | Rolls Royce Plc | A stator vane arrangement and a method of casting a stator vane arrangement |
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2015
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US9920651B2 (en) | 2018-03-20 |
EP3045672A1 (en) | 2016-07-20 |
US20160208647A1 (en) | 2016-07-21 |
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